초록 ▼

An inner shroud for a gas turbine engine is described comprising six approximately equiangular segments each segment adapted to securely contain a plurality of vane stems. The segments comprise interlocking first and second sections forming a channel having an aperture suitably sized to securely con

An inner shroud for a gas turbine engine is described comprising six approximately equiangular segments each segment adapted to securely contain a plurality of vane stems. The segments comprise interlocking first and second sections forming a channel having an aperture suitably sized to securely contain the vane stem. The sections when fit together form an outer recess area suitably sized to substantially accommodate the button portion of the vane stem and an inner cavity suitably sized to accommodate the inner portion of the vane stem. This results in reduced shroud curling when used in a split case compressor.

대표청구항 ▼

An inner shroud for a gas turbine engine comprising: six approximately equiangular segments; each segment adapted to securely contain a plurality of variable vane stems; said segment comprising interlocking first and second sections, the first section having a first side wall portion and an outer wa

An inner shroud for a gas turbine engine comprising: six approximately equiangular segments; each segment adapted to securely contain a plurality of variable vane stems; said segment comprising interlocking first and second sections, the first section having a first side wall portion and an outer wall portion, the outer wall portion having an aperture suitably sized to securely contain the vane stem, and the second section having a second side wall portion and an inner wall portion, the sections when fit together forming an outer recess area suitably sized to substantially accommodate the outer portion of the vane stem, and an inner cavity area suitably sized to accommodate the inner portion of the vane stem.